Orbit Optimization for Future Satellite Gravity Field Missions: Influence of the Time Variable Gravity Field Models in a
Many studies in the past have discussed potential orbit configurations of future satellite gravity missions. Most of those works have targeted orbit optimization of the satellite missions of the next generation in the so-called Bender formation. The studi
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Abstract
Many studies in the past have discussed potential orbit configurations of future satellite gravity missions. Most of those works have targeted orbit optimization of the satellite missions of the next generation in the so-called Bender formation. The studies have investigated the impact of the Keplerian orbital parameters, especially the influence of the repeat orbits and mission altitude of both satellite pairs and the inclination of the second pair in Bender formation on the satellite configurations’ gravity field recovery quality performance. Obviously, the search space for the orbit optimization in the Bender formation is vast and, therefore, different approaches have been suggested for optimal orbit design. Among approaches, however, different assumptions about input geophysical models as well as the error models into the simulation software play a role. Our paper shows how different assumptions for input models change the orbit optimization results. For this purpose, the genetic algorithm has been utilized for orbit optimization of the Bender formation where different input models were considered. Those input models include (1) the updated ESA geophysical models, and (2) error models for the Ocean Tide (OT error) and AtmosphereOcean (AO error). Here, we focus on the impact of the models on relative difference of the longitude of ascending nodes between the two pairs in Bender formation. The results of the paper clearly state that our current and future knowledge about signal and error models can significantly affect the orbit optimization problem. Keywords
Genetic algorithm Gravity field recovery Orbit optimization Time-variable gravity field
S. Iran Pour () Department of Geomatics Engineering, Faculty of Civil Engineering and Transportation, University of Isfahan, Isfahan, Iran Institute of Geodesy, University of Stuttgart, Stuttgart, Germany N. Sneeuw Institute of Geodesy, University of Stuttgart, Stuttgart, Germany M. Weigelt Institute of Geodesy, Leibniz University of Hannover, Hannover, Germany A. Amiri-Simkooei Department of Geomatics Engineering, Faculty of Civil Engineering and Transportation, University of Isfahan, Isfahan, Iran Department of Control and Operations, Technical University of Delft, Delft, The Netherlands
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Introduction
Soon after the launch of the Gravity Recovery and Climate Experiment (GRACE) mission (Tapley et al. 2004), several research studies have started to investigate the performance of next generation satellite gravity missions. Those researches range from replacing the GRACE by another inline formation (GRACE Follow-On) or alternative (advanced) formations to analyzing mission scenarios with two pairs, see (Sharifi et al. 2007; Bender et al. 2008; Wiese et al. 2009; Elsaka 2010; Wiese et al. 2012; Ellmer 2011; Elsaka et al. 2012; Iran Pour et al. 2013; Reubelt et al. 2014; Elsaka et al. 2014; Gruber et al. 2014; Klokoˇcník
International Association of Geodesy Symposia, https://doi.org/10.1007/1345_2019_79, © Springer Nature Switzerland AG 2019
S. Iran
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